Class
Article
College
College of Engineering
Faculty Mentor
Douglas Hunsaker
Presentation Type
Oral Presentation
Abstract
Thin-airfoil theory predicts a reduction of section lift when sweep is applied to an infinite wing. This prediction assumes the airfoil sections of the wing are of negligible thickness and the angle of sweep and angle of attack of the wing are small. By relaxing these assumptions, the prediction of section lift of an infinite wing with sweep is generalized to account for a larger variation in airfoil geometry, wing sweep, and flight conditions. The generalized equations derived from the relaxed assumptions are applied to a vortex panel method to obtain section lift predictions for a range of NACA 4-digit airfoils. In an effort to obtain an analytic relationship between the section lift produced by infinite wings with and without sweep, the section lift predictions produced by the vortex panel method are fit to empirical equations. The results are compared to data computed using computational fluid dynamics software.
Location
Room 421
Start Date
4-12-2018 9:00 AM
End Date
4-12-2018 10:15 AM
A Generalization of Thin-Airfoil Theory for Infinite Wings with Sweep
Room 421
Thin-airfoil theory predicts a reduction of section lift when sweep is applied to an infinite wing. This prediction assumes the airfoil sections of the wing are of negligible thickness and the angle of sweep and angle of attack of the wing are small. By relaxing these assumptions, the prediction of section lift of an infinite wing with sweep is generalized to account for a larger variation in airfoil geometry, wing sweep, and flight conditions. The generalized equations derived from the relaxed assumptions are applied to a vortex panel method to obtain section lift predictions for a range of NACA 4-digit airfoils. In an effort to obtain an analytic relationship between the section lift produced by infinite wings with and without sweep, the section lift predictions produced by the vortex panel method are fit to empirical equations. The results are compared to data computed using computational fluid dynamics software.